CA2720088A1 - Burn through resistant aircraft fuselage - Google Patents
Burn through resistant aircraft fuselage Download PDFInfo
- Publication number
- CA2720088A1 CA2720088A1 CA2720088A CA2720088A CA2720088A1 CA 2720088 A1 CA2720088 A1 CA 2720088A1 CA 2720088 A CA2720088 A CA 2720088A CA 2720088 A CA2720088 A CA 2720088A CA 2720088 A1 CA2720088 A1 CA 2720088A1
- Authority
- CA
- Canada
- Prior art keywords
- burnthrough
- aircraft fuselage
- aircraft
- floor
- fuselage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000009413 insulation Methods 0.000 claims abstract description 24
- 239000000463 material Substances 0.000 claims description 22
- 210000001015 abdomen Anatomy 0.000 claims description 14
- 239000011888 foil Substances 0.000 claims description 14
- 239000000835 fiber Substances 0.000 claims description 8
- 239000003365 glass fiber Substances 0.000 claims description 7
- 238000009434 installation Methods 0.000 claims description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 6
- 229910052799 carbon Inorganic materials 0.000 claims description 6
- 230000007704 transition Effects 0.000 claims description 4
- 239000002759 woven fabric Substances 0.000 claims description 4
- 238000012423 maintenance Methods 0.000 description 4
- 239000012774 insulation material Substances 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000035515 penetration Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000010408 film Substances 0.000 description 2
- 239000013589 supplement Substances 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/066—Interior liners
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/18—Floors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention relates to an aircraft fuselage (12) comprising at least one space arranged in the aircraft fuselage and at least one wall (16). According to the invention, the wall resists burnthrough for a period of at least four minutes from outside the aircraft fuselage towards the space, wherein the region of the aircraft fuselage (12) underneath the space does not comprise burnthrough-resistant insulation. The space can be a cargo compartment of the aircraft or a passenger cabin, while the wall can be designed as a cargo compartment floor, passenger cabin floor or wing/fuselage fairing (belly- fairing). The design, according to the invention, of the aircraft fuselage results in burnthrough resistance that meets the requirements of FAR § 25.856 (b) without any additional burnthrough-resistant insulation in the aircraft fuselage.
Description
Burn through resistant aircraft fuselage REFERENCE TO RELATED APPLICATIONS
This application claims the benefit of the filing date of German Patent Application No. 10 2008 016 104.7 filed March 28, 2008 and of United States Provisional Patent Application No. 61/072 320 filed March 28, 2008, the disclosure of which applications is hereby incorporated herein by reference.
TECHNICAL FIELD OF THE INVENTION
The invention relates to an aircraft fuselage.
TECHNOLOGICAL BACKGROUND OF THE INVENTION
Due to recent aviation regulations, in particular FAR 25.856 (b), passenger aircraft with a passenger capacity of 20 or greater must be constructed so that they are burnthrough-resistant. This means that for a period of at least four minutes, flame penetration of the aircraft from the exterior to the interior into the cabin must be prevented, for example if after an emergency landing there is a fire on the outside of the aircraft, which fire acts on the aircraft fuselage.
The aluminium aircraft-structures that are commonly used experience burnthrough after approximately 60 seconds so that after this period of time it is possible for flames acting on the aircraft fuselage to enter the interior of the aircraft.
In order to prevent this, for the purpose of protecting a passenger cabin, bumthrough-resistant insulation materials for the lower half of the passenger fuselage are mandatory.
However, bumthrough-resistant insulation materials that are suitable for this purpose are associated with additional expenditure in the construction of the aircraft, and furthermore result in additional weight because, for example, insulation mats need to comprise special burnthrough-resistant film or foil and film or foil attachment
This application claims the benefit of the filing date of German Patent Application No. 10 2008 016 104.7 filed March 28, 2008 and of United States Provisional Patent Application No. 61/072 320 filed March 28, 2008, the disclosure of which applications is hereby incorporated herein by reference.
TECHNICAL FIELD OF THE INVENTION
The invention relates to an aircraft fuselage.
TECHNOLOGICAL BACKGROUND OF THE INVENTION
Due to recent aviation regulations, in particular FAR 25.856 (b), passenger aircraft with a passenger capacity of 20 or greater must be constructed so that they are burnthrough-resistant. This means that for a period of at least four minutes, flame penetration of the aircraft from the exterior to the interior into the cabin must be prevented, for example if after an emergency landing there is a fire on the outside of the aircraft, which fire acts on the aircraft fuselage.
The aluminium aircraft-structures that are commonly used experience burnthrough after approximately 60 seconds so that after this period of time it is possible for flames acting on the aircraft fuselage to enter the interior of the aircraft.
In order to prevent this, for the purpose of protecting a passenger cabin, bumthrough-resistant insulation materials for the lower half of the passenger fuselage are mandatory.
However, bumthrough-resistant insulation materials that are suitable for this purpose are associated with additional expenditure in the construction of the aircraft, and furthermore result in additional weight because, for example, insulation mats need to comprise special burnthrough-resistant film or foil and film or foil attachment
-2-devices. This in turn, overall, increases the aircraft's weight and thus negatively affects the performance, the economy and maintainability of the aircraft.
Furthermore, the arrangement of insulation mats that comprise burnthrough-resistant film or foil underneath the cargo compartment region (in the bilge of the fuselage) is not recommended, because a considerable amount of humidity collects in this region, which humidity would be absorbed by the insulation mats. This would result in a gradual increase in the weight of the insulation mats, and drainage would be rendered more difficult.
SUMMARY OF THE INVENTION
It is thus the object of the invention to propose an aircraft fuselage that is burnthrough resistant for a period of at least four minutes, in which aircraft fuselage, at least in some regions underneath cargo spaces, there is no need to use insulation mats that are designed to be burnthrough resistant.
The object is met by the characteristics of the independent claims 1, 9, 11 and 13.
Advantageous improvements are provided in the respective subclaims.
Burnthrough resistance in the passenger cabin is provided by a burnthrough-resistant wall that resists burnthrough for a period of at least four minutes from outside the aircraft fuselage into a space in the interior of the aircraft fuselage. In a first embodiment this may be implemented by a burnthrough-resistant cargo compartment floor which achieves corresponding burnthrough resistance in a cargo compartment or in a passenger cabin. Since a passenger cabin of an aircraft is usually arranged above a cargo compartment, if a burnthrough-resistant cargo compartment floor is provided, a fire located underneath the cargo compartment would not be able to penetrate the cargo compartment and thus would also not be able to penetrate the passenger cabin. A suitable burnthrough-resistant cargo compartment floor could comprise cargo-compartment floor panels that are made from suitable materials,
Furthermore, the arrangement of insulation mats that comprise burnthrough-resistant film or foil underneath the cargo compartment region (in the bilge of the fuselage) is not recommended, because a considerable amount of humidity collects in this region, which humidity would be absorbed by the insulation mats. This would result in a gradual increase in the weight of the insulation mats, and drainage would be rendered more difficult.
SUMMARY OF THE INVENTION
It is thus the object of the invention to propose an aircraft fuselage that is burnthrough resistant for a period of at least four minutes, in which aircraft fuselage, at least in some regions underneath cargo spaces, there is no need to use insulation mats that are designed to be burnthrough resistant.
The object is met by the characteristics of the independent claims 1, 9, 11 and 13.
Advantageous improvements are provided in the respective subclaims.
Burnthrough resistance in the passenger cabin is provided by a burnthrough-resistant wall that resists burnthrough for a period of at least four minutes from outside the aircraft fuselage into a space in the interior of the aircraft fuselage. In a first embodiment this may be implemented by a burnthrough-resistant cargo compartment floor which achieves corresponding burnthrough resistance in a cargo compartment or in a passenger cabin. Since a passenger cabin of an aircraft is usually arranged above a cargo compartment, if a burnthrough-resistant cargo compartment floor is provided, a fire located underneath the cargo compartment would not be able to penetrate the cargo compartment and thus would also not be able to penetrate the passenger cabin. A suitable burnthrough-resistant cargo compartment floor could comprise cargo-compartment floor panels that are made from suitable materials,
-3-which floor panels on the one hand feature high strength, while on the other hand providing adequate burnthrough resistance. For example, carbon fibre materials or glass fibre materials may be considered for this, which materials may be applied in the form of woven-fabric structures, laminates, sandwich structures or the like.
Preferably, the weight of the floor panels used in the context of the invention is identical to the weight of conventional cargo-compartment floor panels, so that this does not result in additional weight.
Since cargo compartment floors also comprise regions without floor panels, for example regions that comprise roller conveyors or ball-element mats for the transport of containers, these regions preferably need to be rendered burnthrough resistant with the use of other means. For this purpose, among other things, thin glass fibre mats and/or carbon fibre mats or laminates underneath the above-mentioned structures could be used. Since these particular areas without floor panels cover only a relatively small part of the cargo compartment floor, the production expenditure and also the additional weight resulting from the special burnthrough materials in the regions without floor panels are less than the additional weight after fitting the entire underfloor region of the aircraft with separate burnthrough-resistant insulation mats.
In addition, conventional insulation mats in the underfloor region may become soiled very quickly and may absorb a lot of liquid, which could encourage corrosion and could also negatively affect the characteristics of the product. The use of such insulation mats would also be associated with disadvantages relating to installation and maintenance, because these components are easily damaged so that the production- and maintenance costs are considerably lower with the use of the solution according to the invention than would be achieved with burnthrough-resistant insulation mats.
In a further embodiment of the invention, as an alternative the floor panels of the passenger cabin are designed so that they are burnthrough resistant. To this effect the same materials may be used as for burnthrough protection on the cargo compartment
Preferably, the weight of the floor panels used in the context of the invention is identical to the weight of conventional cargo-compartment floor panels, so that this does not result in additional weight.
Since cargo compartment floors also comprise regions without floor panels, for example regions that comprise roller conveyors or ball-element mats for the transport of containers, these regions preferably need to be rendered burnthrough resistant with the use of other means. For this purpose, among other things, thin glass fibre mats and/or carbon fibre mats or laminates underneath the above-mentioned structures could be used. Since these particular areas without floor panels cover only a relatively small part of the cargo compartment floor, the production expenditure and also the additional weight resulting from the special burnthrough materials in the regions without floor panels are less than the additional weight after fitting the entire underfloor region of the aircraft with separate burnthrough-resistant insulation mats.
In addition, conventional insulation mats in the underfloor region may become soiled very quickly and may absorb a lot of liquid, which could encourage corrosion and could also negatively affect the characteristics of the product. The use of such insulation mats would also be associated with disadvantages relating to installation and maintenance, because these components are easily damaged so that the production- and maintenance costs are considerably lower with the use of the solution according to the invention than would be achieved with burnthrough-resistant insulation mats.
In a further embodiment of the invention, as an alternative the floor panels of the passenger cabin are designed so that they are burnthrough resistant. To this effect the same materials may be used as for burnthrough protection on the cargo compartment
-4-floor. However, the burnthrough protection on the passenger cabin is associated with a very considerable advantage in that even less burnthrough-resistant insulation needs to be provided than is the case in the first embodiment.
In a further embodiment of the present invention, adequate burnthrough protection, at least in the region of the wing/fuselage transition, may be implemented in that the aerodynamic protective fairing provided in that location, also referred to as the "belly fairing" is produced from suitable glass fibre structures or carbon fibre structures, similar to those in the preceding exemplary embodiments. Thus the belly fairing may be modified to the effect that it comprises outstanding characteristics relating to burnthrough resistance. Consequently, in this region too it is possible to do without burnthrough-resistant insulation, which saves weight and also expenditure during manufacture. The detail design of the fairing may have to be modified in some locations so that it may be ensured that flame penetration at the existing gaps in the fairing becomes impossible, and thus, in the case of a fire located underneath the aircraft fuselage and acting from the outside to the inside the passenger cabin is completely protected. These modifications relate, for example, to the reduction in the gap dimensions of the fairing components, to the integration of overlapping areas in fairing components and the like, so that flame penetration cannot occur.
SHORT DESCRIPTION OF THE DRAWINGS
Below, the invention is explained in more detail with reference to figures. In the figures, the same reference characters are used for identical objects. The following are shown:
Fig. 1: a diagrammatic view of the lower fuselage region in the state of the art;
Fig. 2: a diagrammatic view of the lower region of a burnthrough-resistant aircraft fuselage according to the invention;
In a further embodiment of the present invention, adequate burnthrough protection, at least in the region of the wing/fuselage transition, may be implemented in that the aerodynamic protective fairing provided in that location, also referred to as the "belly fairing" is produced from suitable glass fibre structures or carbon fibre structures, similar to those in the preceding exemplary embodiments. Thus the belly fairing may be modified to the effect that it comprises outstanding characteristics relating to burnthrough resistance. Consequently, in this region too it is possible to do without burnthrough-resistant insulation, which saves weight and also expenditure during manufacture. The detail design of the fairing may have to be modified in some locations so that it may be ensured that flame penetration at the existing gaps in the fairing becomes impossible, and thus, in the case of a fire located underneath the aircraft fuselage and acting from the outside to the inside the passenger cabin is completely protected. These modifications relate, for example, to the reduction in the gap dimensions of the fairing components, to the integration of overlapping areas in fairing components and the like, so that flame penetration cannot occur.
SHORT DESCRIPTION OF THE DRAWINGS
Below, the invention is explained in more detail with reference to figures. In the figures, the same reference characters are used for identical objects. The following are shown:
Fig. 1: a diagrammatic view of the lower fuselage region in the state of the art;
Fig. 2: a diagrammatic view of the lower region of a burnthrough-resistant aircraft fuselage according to the invention;
-5-Fig. 3: a section of a cargo-compartment floor region comprising a roller conveyor;
Figs 4a to c: a belly fairing of a burnthrough-resistant aircraft fuselage according to the invention.
DETAILLED DESCRIPTION OF EXEMPLARY EMBODIMENTS
Fig. 1 in an exemplary manner shows a section of an aircraft fuselage 4 that comprises a cargo compartment floor 2 which is connected to an exterior skin 8 by way of various structural components 6. The state of the art provides for establishing burnthrough resistance in that the exterior skin 8 comprises burnthrough-resistant fuselage insulation 10. This fuselage insulation 10 could, for example, comprise insulating packages comprising a special burnthrough-resistant material, which insulating packages may satisfy the requirements for burnthrough resistance at least for the mandatory period of 4 minutes. The burnthrough-resistant fuselage insulation 10 makes possible evacuation of an aircraft, for example after an emergency landing, which evacuation should be completed in considerably less time than it takes a fire located outside the aircraft fuselage 4 to penetrate the fuselage.
The aircraft fuselage 12 according to the invention, which aircraft fuselage 12 is shown in Fig. 2, in the first exemplary embodiment comprises burnthrough-resistant cargo-compartment floor panels 16 on the cargo space floor 14, which cargo-compartment floor panels 16 extend over a large region of the width of the cargo compartment floor. However, some regions of the cargo compartment floor do not comprise floor panels 16, but instead are equipped with roller conveyors 18 and ball-element mats 20 for easy displacement of containers within the cargo compartment.
In these regions, burnthrough resistance may be achieved only with the use of other measures, for example by integrating burnthrough-resistant film or foil underneath the roller conveyors 18, ball-element mats 20 or other installations. Overall, in this way the entire cargo compartment floor 14 may be constructed so as to be
Figs 4a to c: a belly fairing of a burnthrough-resistant aircraft fuselage according to the invention.
DETAILLED DESCRIPTION OF EXEMPLARY EMBODIMENTS
Fig. 1 in an exemplary manner shows a section of an aircraft fuselage 4 that comprises a cargo compartment floor 2 which is connected to an exterior skin 8 by way of various structural components 6. The state of the art provides for establishing burnthrough resistance in that the exterior skin 8 comprises burnthrough-resistant fuselage insulation 10. This fuselage insulation 10 could, for example, comprise insulating packages comprising a special burnthrough-resistant material, which insulating packages may satisfy the requirements for burnthrough resistance at least for the mandatory period of 4 minutes. The burnthrough-resistant fuselage insulation 10 makes possible evacuation of an aircraft, for example after an emergency landing, which evacuation should be completed in considerably less time than it takes a fire located outside the aircraft fuselage 4 to penetrate the fuselage.
The aircraft fuselage 12 according to the invention, which aircraft fuselage 12 is shown in Fig. 2, in the first exemplary embodiment comprises burnthrough-resistant cargo-compartment floor panels 16 on the cargo space floor 14, which cargo-compartment floor panels 16 extend over a large region of the width of the cargo compartment floor. However, some regions of the cargo compartment floor do not comprise floor panels 16, but instead are equipped with roller conveyors 18 and ball-element mats 20 for easy displacement of containers within the cargo compartment.
In these regions, burnthrough resistance may be achieved only with the use of other measures, for example by integrating burnthrough-resistant film or foil underneath the roller conveyors 18, ball-element mats 20 or other installations. Overall, in this way the entire cargo compartment floor 14 may be constructed so as to be
6 PCT/EP2009/053122 bumthrough resistant; there is no longer a need to provide the separate insulation 10 shown in Fig. 1.
While in the above arrangement a fire located outside the aircraft fuselage could enter the interior of the aircraft fuselage 12 through the exterior skin 8, it could not however penetrate the cargo compartment floor 2 according to the invention in order to reach a cabin region situated above it.
Fig. 3 shows a region of the cargo compartment floor 2 with a roller conveyor which is laterally adjoined by burnthrough-resistant cargo-compartment floor panels 16. On the underside 22 of the roller conveyor 18 a bumthrough-resistant film or foil 24 is arranged, which supplements the adjacent burnthrough-resistant cargo-compartment floor panels 16 so that a fully closed area results. Preferably, the film or foil 24 overlaps the floor panel 16 in the region of its transition to the roller conveyor 18 so that at this position there is no gap through which a fire projecting into the cargo space could penetrate the cargo compartment floor 14. Apart from the underside 22 of the roller conveyor 18, preferably all the other installations of the cargo compartment floor 14 where no cargo-compartment floor panels 16 may be installed are also equipped with such film or foil.
The bumthrough-resistant film or foil 24 may also be designed as a laminate or a woven fibre material. The thickness of the film or foil 24 is preferably not too thin, so that damaging the film or foil 24 at the time of installation, or when carrying out aircraft maintenance, may be prevented.
A further option for implementing bumthrough protection without the use of burnthrough-resistant insulation is provided by a burnthrough-resistant design of the wing/fuselage fairing 26, also referred to as the "belly fairing", of an aircraft 28, which fairing 26 is diagrammatically shown in Figs 4a to 4c in front view and lateral view of the aircraft 28, and in a detailed view of the fairing 26. The belly fairing 26
While in the above arrangement a fire located outside the aircraft fuselage could enter the interior of the aircraft fuselage 12 through the exterior skin 8, it could not however penetrate the cargo compartment floor 2 according to the invention in order to reach a cabin region situated above it.
Fig. 3 shows a region of the cargo compartment floor 2 with a roller conveyor which is laterally adjoined by burnthrough-resistant cargo-compartment floor panels 16. On the underside 22 of the roller conveyor 18 a bumthrough-resistant film or foil 24 is arranged, which supplements the adjacent burnthrough-resistant cargo-compartment floor panels 16 so that a fully closed area results. Preferably, the film or foil 24 overlaps the floor panel 16 in the region of its transition to the roller conveyor 18 so that at this position there is no gap through which a fire projecting into the cargo space could penetrate the cargo compartment floor 14. Apart from the underside 22 of the roller conveyor 18, preferably all the other installations of the cargo compartment floor 14 where no cargo-compartment floor panels 16 may be installed are also equipped with such film or foil.
The bumthrough-resistant film or foil 24 may also be designed as a laminate or a woven fibre material. The thickness of the film or foil 24 is preferably not too thin, so that damaging the film or foil 24 at the time of installation, or when carrying out aircraft maintenance, may be prevented.
A further option for implementing bumthrough protection without the use of burnthrough-resistant insulation is provided by a burnthrough-resistant design of the wing/fuselage fairing 26, also referred to as the "belly fairing", of an aircraft 28, which fairing 26 is diagrammatically shown in Figs 4a to 4c in front view and lateral view of the aircraft 28, and in a detailed view of the fairing 26. The belly fairing 26
-7-is primarily designed to keep the transition between the wing roots and the aircraft fuselage aerodynamically as smooth as possible so that airflow losses in this region are kept within limits. A burnthrough-resistant design of this belly fairing eliminates, at least in this region of the fuselage 12 according to the invention, the need for additional insulation mats on the inside, and thus supplements the burnthrough-resistant cargo compartment floor 14 in the fuselage regions adjacent to the belly fairing 26.
The selection of materials for the belly fairing 26 may be handled very flexibly, because by means of a corresponding additional auxiliary structure 30 the belly fairing 26 is given adequate stability. It is not necessary for the material of the outer skin of the belly fairing 26 to provide the mechanical stability by itself, so that consequently there are no restrictions in the selection of materials.
Preferably a woven glass-fibre material or a woven carbon-fibre material is used, in which as a result of corresponding tests an adequate period of resistance to burnthrough, namely at least four minutes, has been demonstrated.
Lastly, apart from equipping a cargo compartment floor 14 with bumthrough-resistant floor panels 16 and burnthrough-resistant film or foil 24, equipping a passenger cabin floor that is arranged above it is imaginable and sensible where in some regions no cargo compartment is present or where an underfloor region in the aircraft is used as a passenger cabin, or in order to additionally save materials and costs.
With the measures described, in relation to meeting current bumthrough requirements according to FAR 25.856 (b), without additional bumthrough-resistant insulation bumthrough-protection of an aircraft may be achieved. All the fasteners and special bumthrough-resistant materials in the insulation, which fasteners and materials would otherwise be necessary for this, may be done without.
In this way costs and weight are saved, so that the aircraft, while maintaining an
The selection of materials for the belly fairing 26 may be handled very flexibly, because by means of a corresponding additional auxiliary structure 30 the belly fairing 26 is given adequate stability. It is not necessary for the material of the outer skin of the belly fairing 26 to provide the mechanical stability by itself, so that consequently there are no restrictions in the selection of materials.
Preferably a woven glass-fibre material or a woven carbon-fibre material is used, in which as a result of corresponding tests an adequate period of resistance to burnthrough, namely at least four minutes, has been demonstrated.
Lastly, apart from equipping a cargo compartment floor 14 with bumthrough-resistant floor panels 16 and burnthrough-resistant film or foil 24, equipping a passenger cabin floor that is arranged above it is imaginable and sensible where in some regions no cargo compartment is present or where an underfloor region in the aircraft is used as a passenger cabin, or in order to additionally save materials and costs.
With the measures described, in relation to meeting current bumthrough requirements according to FAR 25.856 (b), without additional bumthrough-resistant insulation bumthrough-protection of an aircraft may be achieved. All the fasteners and special bumthrough-resistant materials in the insulation, which fasteners and materials would otherwise be necessary for this, may be done without.
In this way costs and weight are saved, so that the aircraft, while maintaining an
-8-identical safety standard, may at least achieve the same payload and may at least achieve the same fuel consumption figures. Production and maintenance of the aircraft is considerably simplified, in particular because it is no longer necessary to provide burnthrough-resistant insulation in the region of the underfloor of the aircraft.
In addition, it should be pointed out that "comprising" does not exclude other elements or steps, and "a" or "one" does not exclude a plural number.
Furthermore, it should be pointed out that characteristics or steps which have been described with reference to one of the above exemplary embodiments may also be used in combination with other characteristics or steps of other exemplary embodiments described above. Reference characters in the claims are not to be interpreted as limitations.
In addition, it should be pointed out that "comprising" does not exclude other elements or steps, and "a" or "one" does not exclude a plural number.
Furthermore, it should be pointed out that characteristics or steps which have been described with reference to one of the above exemplary embodiments may also be used in combination with other characteristics or steps of other exemplary embodiments described above. Reference characters in the claims are not to be interpreted as limitations.
-9-List of reference characters:
2 Cargo compartment floor 4 Aircraft fuselage 6 Structural component 8 Exterior skin Insulation material 12 Aircraft fuselage (according to the invention) 14 Cargo compartment floor
2 Cargo compartment floor 4 Aircraft fuselage 6 Structural component 8 Exterior skin Insulation material 12 Aircraft fuselage (according to the invention) 14 Cargo compartment floor
10 16 Floor panel 18 Roller conveyor Ball-element mat 22 Underside of roller conveyor 24 Burnthrough-resistant film or foil 15 26 Belly fairing (wing/fuselage fairing) 28 Aircraft Auxiliary structure of belly fairing (wing/fuselage fairing)
Claims (12)
1 1. An aircraft fuselage (12), comprising at least one space arranged in the aircraft fuselage (12) with a floor (14), wherein the floor (14) comprises one or several floor panels (16), characterized in that the floor panels (16) resist burnthrough for a period of at least four minutes from outside the aircraft fuselage (12) towards the space, and wherein the region of the aircraft fuselage (12) underneath the floor (14) does not comprise burnthrough-resistant insulation.
2. The aircraft fuselage (12) of claim 1, wherein the space is designed as a cargo compartment.
3. The aircraft fuselage (12) of claim 1, wherein the space is designed as a passenger cabin.
4. The aircraft fuselage (12) of claim 1, with the floor (14) at least in some regions comprising installations (18, 20) whose installation regions cannot be equipped with floor panels (16), wherein on the underside (22) of the installations (18, 20) burnthrough-resistant film or foil (24) is arranged which resists burnthrough for a period of at least four minutes.
5. The aircraft fuselage (12) of claim 4, wherein the burnthrough-resistant film or foil (24) is made to overlap adjacent floor panels (16).
6. The aircraft fuselage (12) of any one of the preceding claims, wherein the floor (14) is designed from carbon fibre materials or glass fibre materials in the form of woven-fabric structures, laminates, sandwich structures or the like.
7. An aircraft fuselage (12), comprising at least one space with a floor (14) arranged in the aircraft fuselage (12) and a fairing (26) of a wing/fuselage transition, characterized in that the fairing (26) resists burnthrough for a period of at least four minutes from outside the aircraft fuselage (12) towards the space, and wherein the region of the space above the fairing (26) does not comprise burnthrough-resistant insulation.
8. A floor panel (16) for a floor (14) in an aircraft, which floor panel (16) resists burnthrough for a period of at least four minutes.
9. The floor panel (16) of claim 9, wherein the floor panel (16) is designed from carbon fibre materials or glass fibre materials in the form of woven-fabric structures, laminates, sandwich structures or the like.
10. A wing/fuselage fairing or belly fairing of an aircraft with a wall (26) that resists burnthrough into the aircraft fuselage (12) for a period of at least four minutes.
11. The wing/fuselage fairing or belly fairing of claim 10, wherein the wall (26) is designed from carbon fibre materials or glass fibre materials in the form of woven-fabric structures, laminates, sandwich structures or the like.
12. An aircraft with an aircraft fuselage of any one of claims 1-7.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US7232008P | 2008-03-28 | 2008-03-28 | |
| DE102008016104.7 | 2008-03-28 | ||
| US61/072,320 | 2008-03-28 | ||
| DE102008016104A DE102008016104A1 (en) | 2008-03-28 | 2008-03-28 | Breathable aircraft fuselage |
| PCT/EP2009/053122 WO2009118256A2 (en) | 2008-03-28 | 2009-03-17 | Burn through resistant aircraft fuselage |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2720088A1 true CA2720088A1 (en) | 2009-10-01 |
| CA2720088C CA2720088C (en) | 2017-11-28 |
Family
ID=41051287
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2720088A Active CA2720088C (en) | 2008-03-28 | 2009-03-17 | Burn through resistant aircraft fuselage |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US9878770B2 (en) |
| EP (1) | EP2257466B1 (en) |
| JP (1) | JP5539955B2 (en) |
| CN (1) | CN101977810B (en) |
| BR (1) | BRPI0906234A8 (en) |
| CA (1) | CA2720088C (en) |
| DE (1) | DE102008016104A1 (en) |
| RU (1) | RU2502634C2 (en) |
| WO (1) | WO2009118256A2 (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102012005353A1 (en) * | 2012-03-16 | 2013-09-19 | Airbus Operations Gmbh | Aircraft fuselage structure with transverse profiles and truss structure |
| FR3000020B1 (en) * | 2012-12-26 | 2015-01-30 | Airbus Operations Sas | FUSELAGE AIRCRAFT PROVIDED WITH SIDE EXCREASES DELIMINATING STORAGE SPACES |
| ES2578427T3 (en) | 2012-12-27 | 2016-07-26 | Airbus Operations S.L. | An ventral fairing of an aircraft with improved storage capacity |
| CN105923144B (en) * | 2016-05-30 | 2018-08-21 | 中国商用飞机有限责任公司 | Fire-resistance flame burns fuselage and burns the fire-resistance flame burn-through floor of fuselage for fire-resistance flame |
| US11459085B2 (en) * | 2019-04-30 | 2022-10-04 | Textron Innovations Inc. | Energy attenuation stabilizers and methods |
| CN112937833A (en) * | 2021-03-05 | 2021-06-11 | 中国商用飞机有限责任公司 | Airframe structure for aircraft, construction method thereof and aircraft |
Family Cites Families (46)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4557961A (en) * | 1983-05-27 | 1985-12-10 | The Boeing Company | Light-weight, fire-retardant structural panel |
| WO1985003032A1 (en) * | 1984-01-09 | 1985-07-18 | The Boeing Company | Composite material structure with integral fire protection |
| JPS62189251A (en) * | 1986-02-13 | 1987-08-19 | 川崎重工業株式会社 | Floor structure |
| FR2693976B1 (en) * | 1992-07-22 | 1994-09-30 | Eurocopter France | Fuselage structure for helicopter. |
| DE4313592C2 (en) * | 1993-04-26 | 2000-02-17 | Daimler Chrysler Aerospace | Wide-body aircraft |
| JPH07329197A (en) | 1994-04-13 | 1995-12-19 | Nikkiso Co Ltd | Vehicle, honeycomb laminar structure, interior fittings, architecture and panel |
| IT1276840B1 (en) * | 1994-04-14 | 1997-11-03 | Eurocompositi Srl | INCOMBUSTIBLE PANEL AND METHOD FOR ITS OBTAINING |
| US6029933A (en) * | 1997-08-01 | 2000-02-29 | The Boeing Company | Fire resistant pressure relief panel assembly |
| US6322022B1 (en) * | 1998-11-16 | 2001-11-27 | Johns Manville International, Inc. | Burn through resistant systems for transportation, especially aircraft |
| US6611659B2 (en) * | 1999-04-24 | 2003-08-26 | Airbus Deutschland Gmbh | Electrically heated aircraft composite floor panel |
| AUPQ100799A0 (en) * | 1999-06-17 | 1999-07-08 | Green Peaks Pty Ltd | Fire barrier panel |
| US6834159B1 (en) * | 1999-09-10 | 2004-12-21 | Goodrich Corporation | Aircraft heated floor panel |
| EP1873059A3 (en) | 2000-06-06 | 2012-04-11 | Mitsubishi Heavy Industries, Ltd. | Airplane with multi-level cabins for cargos or passengers and method of loading cargos into same |
| ATE318207T1 (en) * | 2000-12-29 | 2006-03-15 | Lg Chemical Ltd | FIREPROOF COMPOSITE PANELS AND DECORATIVE FIREPROOF COMPOSITE PANELS USING SAME |
| US20020195525A1 (en) * | 2001-06-21 | 2002-12-26 | Anton Claire E. | Spray on-foam insulation system for an aircraft |
| US6863980B2 (en) * | 2002-10-08 | 2005-03-08 | The Boeing Company | Monolithic composite firewall |
| WO2004081103A2 (en) | 2003-03-10 | 2004-09-23 | Solvay Advanced Polymers, L.L.C. | Method for lowering the melt viscosity of an aromatic sulfone polymer composition, and method for manufacturing an aircraft component |
| DE10324648B4 (en) | 2003-05-30 | 2008-01-10 | Airbus Deutschland Gmbh | Device for receiving lashing devices for a freight loading system of a means of transport, in particular of an aircraft |
| FR2859943B1 (en) * | 2003-09-23 | 2007-07-13 | Rhodia Industrial Yarns Ag | COMPOSITE STRUCTURE |
| DE102004001081B4 (en) * | 2004-01-05 | 2013-02-14 | Airbus Operations Gmbh | Insulation structure for the internal insulation of a vehicle |
| US7284726B2 (en) * | 2004-02-17 | 2007-10-23 | Sikorsky Aircraft Corporation | Self extinguishing composite primary structure |
| FR2871436B1 (en) * | 2004-06-11 | 2007-09-07 | Airbus France Sas | AIRCRAFT PROVIDED WITH A VENTRAL CARENAGE AND VENTRAL CARENAGE. |
| US20060046598A1 (en) * | 2004-08-27 | 2006-03-02 | Orcon Corporation | Light weight fire-blocking insulation blanket with improved durability and handleability |
| US7988809B2 (en) * | 2004-09-01 | 2011-08-02 | Hexcel Corporation | Aircraft floor and interior panels using edge coated honeycomb |
| US7182291B2 (en) * | 2005-03-23 | 2007-02-27 | The Boeing Company | Integrated aircraft structural floor |
| US7291373B2 (en) * | 2005-05-05 | 2007-11-06 | Northrop Grumman Corporation | Thermally insulated structure—full depth sandwich joint concept |
| DE102005044378A1 (en) | 2005-09-16 | 2007-03-22 | Airbus Deutschland Gmbh | Commercial or military aircraft fuselage increasing safety of passengers subject to threats, includes layer resisting projectile penetration |
| US8360362B2 (en) * | 2006-02-21 | 2013-01-29 | The Boeing Company | Aircraft floor and method of assembly |
| DE102006020147A1 (en) * | 2006-05-02 | 2007-11-15 | Airbus Deutschland Gmbh | Fire barrier for aircraft to protect from burn-out between cargo and passenger cab, has burnout-safety-panel for blocking fire in partition wall area of aircraft body |
| US7977263B2 (en) * | 2006-05-26 | 2011-07-12 | Glass Incorporated | Glass fiber for high temperature insulation |
| US8651423B2 (en) * | 2006-09-06 | 2014-02-18 | Airbus Operations Gmbh | Fireproof bulkhead of a highly porous structure with intumescent coating and method for its production |
| ES2317762B1 (en) * | 2006-10-31 | 2010-02-10 | Airbus España, S.L. | VENTRAL MEAT FOR AN AIRCRAFT. |
| DE102007046479B4 (en) * | 2006-12-13 | 2015-08-27 | Airbus Operations Gmbh | Fire protection device for an aircraft or spacecraft |
| WO2008136875A1 (en) * | 2007-01-08 | 2008-11-13 | Unifrax I Llc | Fire-barrier film laminate |
| DE102007003357A1 (en) * | 2007-01-17 | 2008-07-24 | Airbus Deutschland Gmbh | Method for bonding a thermoplastic material to a fiber composite material |
| US8398027B2 (en) * | 2007-09-17 | 2013-03-19 | The Boeing Company | Method and apparatus for reinforcing composite structures |
| EP2203308A4 (en) * | 2007-10-16 | 2012-11-28 | 3M Innovative Properties Co | Flexible laminate sheet materials |
| US8056850B2 (en) * | 2008-01-18 | 2011-11-15 | The Boeing Company | Particle-filled wing-to-body fairing and method for reducing fairing vibrations |
| US8292214B2 (en) * | 2008-01-18 | 2012-10-23 | The Boeing Company | Vibration damping for wing-to-body aircraft fairing |
| WO2009134299A2 (en) * | 2008-03-14 | 2009-11-05 | Kaneka Corporation | Fire barrier protection for airplanes comprising graphite films |
| JP5799021B2 (en) * | 2009-11-23 | 2015-10-21 | アプライド ナノストラクチャード ソリューションズ リミテッド ライアビリティー カンパニーＡｐｐｌｉｅｄ Ｎａｎｏｓｔｒｕｃｔｕｒｅｄｓｏｌｕｔｉｏｎｓ， Ｌｌｃ | Aviation-based composite material structure adapted to CNT |
| DE102009054886A1 (en) * | 2009-12-17 | 2011-06-22 | Airbus Operations GmbH, 21129 | Fire protection system, aircraft or spacecraft and method for containing and suppressing a fire |
| DE102010019382A1 (en) * | 2010-05-04 | 2011-11-10 | Airbus Operations Gmbh | Thermal insulating tape with fire protection function and its application in aircraft construction |
| BR112013012230A2 (en) * | 2010-11-19 | 2018-01-30 | Lamart Corp | fire barrier layer and fire barrier film laminate |
| EP2701809A4 (en) * | 2011-04-29 | 2014-10-29 | Unifrax I Llc | Burnthrough protection system |
| US20130045352A1 (en) * | 2011-08-15 | 2013-02-21 | Charles Francis Kern | Non-woven fire barrier mat |
-
2008
- 2008-03-28 DE DE102008016104A patent/DE102008016104A1/en not_active Ceased
-
2009
- 2009-03-17 CN CN200980110273.9A patent/CN101977810B/en active Active
- 2009-03-17 WO PCT/EP2009/053122 patent/WO2009118256A2/en active Application Filing
- 2009-03-17 CA CA2720088A patent/CA2720088C/en active Active
- 2009-03-17 BR BRPI0906234A patent/BRPI0906234A8/en not_active IP Right Cessation
- 2009-03-17 JP JP2011501176A patent/JP5539955B2/en not_active Expired - Fee Related
- 2009-03-17 US US12/935,107 patent/US9878770B2/en active Active
- 2009-03-17 RU RU2010141786/11A patent/RU2502634C2/en not_active IP Right Cessation
- 2009-03-17 EP EP09724077.4A patent/EP2257466B1/en not_active Not-in-force
Also Published As
| Publication number | Publication date |
|---|---|
| EP2257466A2 (en) | 2010-12-08 |
| US9878770B2 (en) | 2018-01-30 |
| JP2011515272A (en) | 2011-05-19 |
| DE102008016104A1 (en) | 2009-10-08 |
| CN101977810A (en) | 2011-02-16 |
| JP5539955B2 (en) | 2014-07-02 |
| BRPI0906234A8 (en) | 2015-09-22 |
| CA2720088C (en) | 2017-11-28 |
| WO2009118256A2 (en) | 2009-10-01 |
| BRPI0906234A2 (en) | 2015-06-30 |
| WO2009118256A4 (en) | 2010-01-28 |
| EP2257466B1 (en) | 2016-12-21 |
| RU2502634C2 (en) | 2013-12-27 |
| CN101977810B (en) | 2016-04-20 |
| US20110121133A1 (en) | 2011-05-26 |
| WO2009118256A3 (en) | 2009-11-26 |
| RU2010141786A (en) | 2012-05-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2720088C (en) | Burn through resistant aircraft fuselage | |
| EP2121433B1 (en) | Fuselage structural component of an aircraft or spacecraft, with a foam layer as thermal insulation | |
| US8245972B2 (en) | Leading edge for aircraft wings and empennages | |
| US20080283664A1 (en) | Aircraft Fuselage Structure | |
| JP2007521184A (en) | Panel arrangement for interior lining of cabin in aircraft | |
| US20180334237A1 (en) | Aircraft Monument Having a Secondary Security Door | |
| WO2007031321B1 (en) | Aircraft fuselage | |
| US20100090061A1 (en) | Fuselage of an aircraft or spacecraft of crp/metal hybrid construction with a metal framework | |
| CA2883992C (en) | Structure and method for reducing air flow in a wall volume of an aircraft | |
| US8899523B2 (en) | Fire protection space for aircraft passengers provided with the aid of fuselage skin of fibre-metal laminates | |
| CA2935048C (en) | Methods, systems and apparatus for lining an aircraft cargo compartment | |
| US20210147063A1 (en) | Fireproof and thermal insulator product | |
| US20230060580A1 (en) | System and method for passenger plane to cargo plane conversion | |
| CN201633918U (en) | Passenger-cargo mixed airplane passenger cabin |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request |
Effective date: 20140122 |